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HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il)
Reynolds number: 50,000
Max Cl/Cd: 30.15 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3014-il-50000.txt
Download as CSV file: xf-hq3014-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/14 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3060   0.10719   0.10052  -0.0286   1.0000   0.3304
  -9.000  -0.3074   0.10494   0.09836  -0.0268   1.0000   0.3436
  -8.750  -0.3176   0.10341   0.09694  -0.0245   1.0000   0.3553
  -8.500  -0.3432   0.10368   0.09737  -0.0211   1.0000   0.3674
  -8.250  -0.3321   0.10043   0.09414  -0.0188   1.0000   0.3812
  -8.000  -0.3319   0.09833   0.09209  -0.0159   1.0000   0.3956
  -7.750  -0.3317   0.09618   0.08999  -0.0131   1.0000   0.4088
  -7.000  -0.5968   0.07019   0.06427  -0.0356   1.0000   0.1644
  -6.750  -0.6126   0.06278   0.05627  -0.0382   1.0000   0.1505
  -6.500  -0.6063   0.05855   0.05184  -0.0378   1.0000   0.1492
  -6.250  -0.5984   0.05427   0.04725  -0.0377   1.0000   0.1480
  -6.000  -0.5882   0.05010   0.04247  -0.0382   1.0000   0.1491
  -5.750  -0.5734   0.04638   0.03818  -0.0384   1.0000   0.1510
  -5.500  -0.5567   0.04403   0.03585  -0.0377   1.0000   0.1565
  -5.250  -0.5376   0.04143   0.03272  -0.0376   1.0000   0.1620
  -5.000  -0.5168   0.03899   0.02973  -0.0375   1.0000   0.1668
  -4.750  -0.4972   0.03737   0.02807  -0.0368   1.0000   0.1745
  -4.500  -0.4745   0.03564   0.02579  -0.0364   1.0000   0.1799
  -4.250  -0.4543   0.03425   0.02441  -0.0357   1.0000   0.1888
  -4.000  -0.4329   0.03306   0.02302  -0.0350   1.0000   0.1993
  -3.750  -0.4112   0.03206   0.02185  -0.0341   1.0000   0.2106
  -3.500  -0.3906   0.03118   0.02097  -0.0332   1.0000   0.2272
  -3.250  -0.3708   0.03027   0.02026  -0.0322   1.0000   0.2485
  -3.000  -0.3504   0.02931   0.01950  -0.0312   1.0000   0.2828
  -2.750  -0.3293   0.02769   0.01889  -0.0306   1.0000   0.3781
  -2.500  -0.3302   0.02790   0.02059  -0.0221   1.0000   0.6380
  -2.250  -0.3310   0.02875   0.02151  -0.0143   1.0000   0.7166
  -2.000  -0.3297   0.02920   0.02192  -0.0077   1.0000   0.7675
  -1.750  -0.3274   0.02935   0.02200  -0.0017   1.0000   0.8110
  -1.500  -0.3244   0.02929   0.02189   0.0040   1.0000   0.8541
  -1.250  -0.3141   0.02923   0.02180   0.0083   1.0000   0.9027
  -1.000  -0.1552   0.03266   0.02464  -0.0142   1.0000   1.0000
  -0.750  -0.1622   0.03197   0.02388  -0.0115   1.0000   1.0000
  -0.500  -0.1680   0.03127   0.02311  -0.0089   1.0000   1.0000
  -0.250  -0.1585   0.03112   0.02280  -0.0090   0.9971   1.0000
   0.000  -0.1204   0.03211   0.02355  -0.0140   0.9855   1.0000
   0.250  -0.0824   0.03315   0.02437  -0.0186   0.9734   1.0000
   0.500  -0.0462   0.03418   0.02518  -0.0227   0.9617   1.0000
   0.750  -0.0084   0.03532   0.02612  -0.0269   0.9491   1.0000
   1.000   0.0299   0.03653   0.02715  -0.0309   0.9365   1.0000
   1.250   0.0688   0.03778   0.02822  -0.0349   0.9232   1.0000
   1.500   0.1076   0.03903   0.02933  -0.0386   0.9095   1.0000
   1.750   0.1452   0.04021   0.03037  -0.0419   0.8947   1.0000
   2.000   0.1811   0.04132   0.03138  -0.0447   0.8794   1.0000
   2.250   0.2145   0.04234   0.03229  -0.0469   0.8633   1.0000
   2.500   0.2471   0.04334   0.03322  -0.0489   0.8469   1.0000
   2.750   0.2793   0.04434   0.03415  -0.0507   0.8305   1.0000
   3.000   0.3109   0.04533   0.03508  -0.0523   0.8144   1.0000
   3.250   0.3418   0.04628   0.03600  -0.0537   0.7981   1.0000
   3.500   0.3721   0.04723   0.03692  -0.0549   0.7818   1.0000
   3.750   0.4022   0.04815   0.03783  -0.0559   0.7655   1.0000
   4.000   0.4325   0.04903   0.03871  -0.0569   0.7489   1.0000
   4.250   0.4635   0.04984   0.03954  -0.0578   0.7322   1.0000
   4.500   0.4957   0.05057   0.04028  -0.0586   0.7155   1.0000
   4.750   0.5297   0.05113   0.04088  -0.0594   0.6988   1.0000
   5.000   0.5653   0.05152   0.04133  -0.0601   0.6822   1.0000
   5.250   0.6023   0.05171   0.04158  -0.0607   0.6659   1.0000
   5.500   0.6276   0.05227   0.04218  -0.0603   0.6482   1.0000
   5.750   0.6455   0.05315   0.04313  -0.0594   0.6292   1.0000
   6.000   0.6730   0.05353   0.04358  -0.0590   0.6119   1.0000
   6.250   0.7035   0.05365   0.04378  -0.0586   0.5952   1.0000
   6.500   0.7359   0.05352   0.04376  -0.0581   0.5789   1.0000
   6.750   0.7678   0.05330   0.04364  -0.0575   0.5632   1.0000
   7.000   0.8018   0.05276   0.04320  -0.0567   0.5478   1.0000
   7.250   0.8375   0.05188   0.04246  -0.0557   0.5330   1.0000
   7.500   0.8791   0.05022   0.04094  -0.0546   0.5186   1.0000
   7.750   0.9408   0.04690   0.03781  -0.0544   0.5043   1.0000
   8.000   1.0383   0.04170   0.03281  -0.0576   0.4863   1.0000
   8.250   1.1052   0.03931   0.03043  -0.0596   0.4655   1.0000
   8.500   1.1214   0.04021   0.03140  -0.0577   0.4464   1.0000
   8.750   1.1509   0.04051   0.03175  -0.0571   0.4270   1.0000
   9.000   1.2020   0.03987   0.03095  -0.0585   0.4056   1.0000
   9.250   1.2159   0.04126   0.03243  -0.0566   0.3887   1.0000
   9.500   1.2306   0.04260   0.03384  -0.0549   0.3722   1.0000
   9.750   1.2465   0.04398   0.03532  -0.0533   0.3563   1.0000
  10.000   1.2619   0.04539   0.03679  -0.0517   0.3407   1.0000
  10.250   1.2772   0.04687   0.03833  -0.0501   0.3257   1.0000
  10.500   1.2923   0.04842   0.03993  -0.0485   0.3111   1.0000
  10.750   1.3073   0.05000   0.04156  -0.0470   0.2966   1.0000
  11.000   1.3234   0.05166   0.04328  -0.0456   0.2824   1.0000
  11.250   1.3020   0.05481   0.04673  -0.0411   0.2751   1.0000
  11.500   1.0553   0.07947   0.07163  -0.0361   0.3024   1.0000
  11.750   1.0982   0.07699   0.06931  -0.0335   0.2877   1.0000
  12.000   1.0438   0.08877   0.08105  -0.0364   0.2844   1.0000
  12.250   0.8385   0.12865   0.12037  -0.0573   0.3087   1.0000
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